CN205686604U - A kind of telescopic folding wings of the span - Google Patents
A kind of telescopic folding wings of the span Download PDFInfo
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- CN205686604U CN205686604U CN201620539010.7U CN201620539010U CN205686604U CN 205686604 U CN205686604 U CN 205686604U CN 201620539010 U CN201620539010 U CN 201620539010U CN 205686604 U CN205686604 U CN 205686604U
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- wing
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- inner wing
- pedestal
- span
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Abstract
The open a kind of telescopic folding wings of the span of this utility model, including front wing, rear wing, pedestal and actuating system, front wing includes inner wing before symmetrically arranged left front inner wing and the right side, rear wing includes the symmetrically arranged left back wing and right rear wing, before left front inner wing and the right side, the end of inner wing is installed axle by front wing and is hingedly mounted on pedestal one end, other end device actuating system at pedestal, outer wing before the left front outer wing slided along its length and the right side it is respectively provided with on inner wing before left front inner wing and the right side, one end of the left back wing and right rear wing is hingedly mounted on slide block, before the other end of the left back wing and right rear wing and left front outer wing and the right side, outer wing is articulated and connected, slide block is driven along pedestal the most movable by actuating system.This utility model span amplitude of variation is big, by wing and lean against on pedestal during gathering, takes up room little, left front inner wing, right before inner wing around front wing, axle rotary expansion is installed, the most left and right front outer wing increases span-width, increases lift and lift-drag ratio, improves flight efficiency.
Description
Technical field
This utility model relates to folding wings technical field, particularly relates to a kind of telescopic folding wings of the span.
Background technology
Comparing rotor craft, Fixed Wing AirVehicle has the higher feature of flight efficiency, so general aircraft is (such as war
Bucket machine, airline carriers of passengers, cruise missile and stand-off bomb) use fixed-wing to provide device as prevailing lift more.Fixed-wing flies
The span of device is the key parameter affecting aircraft lift, and its span is the biggest, the liter that under square one, this aircraft produces
Power is the biggest, and lift-drag ratio (lift and the ratio of resistance) is the biggest, and aircraft flight efficiency is the highest, so passenger plane and transporter
Often there is a pair wing the biggest.Although the flight efficiency of fixed-wing is higher, but to there is also it intrinsic for general fixed-wing
Shortcoming, as in the case of not considering telescopic folding, its span is the biggest, and aircraft needs to occupy the space parked and store more
Greatly, this is often improper the most feasible for the aircraft of some specific uses, as usual in aircraft carrier airplane carrier fighter
Require that its wing design becomes folding form；The airborne Cruise Missile launched of throwing in often also requires that its missile wing is designed to roll over
Folded, to facilitate carry to aircraft launcher；Cartridge type or the unmanned plane of canister launch and Cruise Missile, in order to enable smoothly unmanned plane
Or Cruise Missile puts into firing box or launching tube, majority also requires that its wing (or missile wing) is designed as contractile folding wings.
Traditional folding wings mainly has two kinds of structures, and one is double section single lap aerofoils, and when storing, outer wing is upwards rolled over
Rise, thus reduce and laterally take up room；Another kind is rhombus wing structure, mainly has four wings mutually to support to form rhombus, changes
Angle realizes receiving the wing and spademan.But the span amplitude of variation of tradition folding wings is limited, it is difficult to realize the wing of the big span, receiving
Also being difficult to when the wing stores taper to minimum by taking up room, range of application is limited.
Utility model content
The technical assignment of technical problem to be solved in the utility model and proposition is to improve prior art, it is provided that
A kind of telescopic folding wings of the span, solves the span amplitude of variation of tradition folding wings in current technology limited, it is difficult to realize big
The span of amplitude also cannot effectively reduce the problem taken up room.
For solving above technical problem, the technical solution of the utility model is:
A kind of telescopic folding wings of the span, including front wing, rear wing, pedestal and actuating system, it is characterised in that described
Front wing includes inner wing before symmetrically arranged left front inner wing and the right side, and rear wing includes the symmetrically arranged left back wing and right rear wing, left front interior
Before the wing and the right side, the end of inner wing is installed axle by front wing and is hingedly mounted on pedestal one end, in the other end device start system of pedestal
System, one end of the left back wing and right rear wing is hingedly mounted on slide block by rear wing installation axle, and slide block is driven along base by actuating system
Seat is longitudinally movable, and the other end of the left back wing and right rear wing slides also along the length direction of inner wing before left front inner wing and the right side respectively
Before driving left front inner wing and the right side, inner wing launches or draws in；When rounding state, actuating system makes left front along pedestal longitudinal contraction
Before inner wing and the right side, inner wing, the left back wing and right rear wing respectively and are close together, left front inner wing, right front inner wing, the left back wing and right rear wing
It is positioned at the longitudinal direction of pedestal；Upon deployment, actuating system promotes slide block, the left back wing, right rear wing and left front along pedestal longitudinal tensile strain
The both sides expansion that inner wing, right front interior flapwise pedestal are longitudinal, left front inner wing, right front inner wing rotate, around front wing installation axle, the exhibition extremely set
Angle of release degree reaches maximum span state.
The telescopic folding wings of the span described in the utility model can realize receiving the wing and spademan to greatest extent, the left back wing and
Slide along the length direction of inner wing before left front inner wing and the right side in the end of right rear wing, so that inner wing is being received before left front inner wing and the right side
Can and lean against in the longitudinal direction of pedestal when holding together so that taking up room of storing minimizes；Simultaneously when spademan, so that left front
Inner wing, right front inner wing rotate and realize maximum span-width to set angle, and span amplitude of variation is big, is effectively improved aircraft product
Raw lift, improves the flight efficiency of aircraft.
Further, before described left front inner wing and the right side, on inner wing, it is respectively provided with outer wing before left front outer wing and the right side, left back
Before arranging trundle and left front outer wing and the right side on the wing and right rear wing, outer wing is articulated and connected, and before left front outer wing and the right side outer wing is respectively
Slide along inner wing length direction before left front inner wing and the right side under the drive of the left back wing and right rear wing, upon deployment, left front outer wing and
Before right outer wing respectively before left front inner wing and the right side length direction of inner wing stretch out increase span-width.
This utility model, by arranging outer wing before left front outer wing and the right side, can further strengthen span width upon deployment
Degree, improves the lift of aircraft greatly, improves flight efficiency.
Further, inner chamber along its length, left front outer wing and the right side are set on inner wing before described left front inner wing and the right side
Front outer wing device respectively slides in the inner chamber of inner wing before left front inner wing and the right side along its length；Or outside before left front outer wing and the right side
The wing be wrapped in left front inner wing and the right side respectively before the periphery of inner wing sliding along its length.Two kinds of structures all make left front inner wing
And formed between outer wing before left front outer wing, right front inner wing and the right side and guide the structure slided so that before left front outer wing and the right side, outer wing divides
Not along the length direction sliding extension of inner wing before left front inner wing and the right side, increasing while span-width outside before left front outer wing and the right side
The wing can also draw in before left front inner wing and the right side on inner wing respectively, will not take exceptional space, ensures that having storing of minimum accounts for
Use space.
Further, described pedestal being provided with elastic limit device, elastic limit device is positioned at front wing and installs next to axis
And before left front inner wing and the right side, inner wing draws the side in direction in, and elastic limit device includes spring leaf and limited block, on pedestal
Offering groove, spring leaf is placed in groove, and limited block is placed in groove and is pressed on spring leaf, and limited block passes through stop screw
Being connected on pedestal, limited block has up and down stroke, and before left front inner wing and the right side, inner wing is when not up to maximum span state,
Before left front inner wing and the right side, limited block is pushed down and is made spring leaf compress by inner wing；Before left front inner wing and the right side, inner wing reaches maximum span shape
During state, limited block pops up the inner side edge of inner wing before abutting against left front inner wing and the right side under spring leaf effect and locks maximum span
State.Before this utility model uses elastic limit device to make left front inner wing and the right side, inner wing can after arriving maximum span angle
Keep pinning this state, it is to avoid in flight course, before left front inner wing and the right side, inner wing generation resilience causes span amplitude to change
And affect flight efficiency, improve the stability in use of aircraft.
Further, on pedestal, before left front inner wing and the right side, the side of inner wing expansion direction is provided with pedestal confined planes,
Before left front inner wing and the right side, inner wing installs axle rotary expansion around front wing, and before left front inner wing and the right side, the outer side edges of inner wing is resisted against pedestal limit
Reaching maximum span state time on plane, before preventing left front inner wing and the right side, inner wing crosses rotation, it is ensured that inner wing before left front inner wing and the right side
Rotary expansion is to the span amplitude set, and remains maximum span angle.
Further, described pedestal being provided with along longitudinal guide chute, slide block slides along guide chute, it is ensured that sliding
The block direction of motion is accurate, it is possible to stable expansion wing.
Further, described actuating system includes start cylinder and start push rod, and start cylinder is fixed on pedestal, makees
Dynamic push rod, along pedestal longitudinal extension simple in construction, takes up room little, easy to use, good stability.
Further, described actuating system uses priming system, gases at high pressure, spring or motor to drive, and type of drive is many
Sample, implements according to the situation of practical flight device, easy to use and flexible.
Further, described slide block is connected with start push rod by contiguous block, and slide block is hinged on even by slide block bearing pin
Connecing on block, contiguous block is hinged on start push rod by connecting bearing pin so that start push rod can exist one when promoting slide block
Fixed play and alignment error, it is to avoid stuck state occurs, it is ensured that wing stably launches or draws in.
Further, described slide block bearing pin is mutually perpendicular to the length direction being connected bearing pin, forms gimbal structure, real
Existing varied angle power transmission, ensures that start push rod is smooth fluent to the active force of slide block, is prevented effectively from and occurs that transmission is stuck
Situation, it is ensured that wing stably launches or draws in.
Compared with prior art, this utility model advantage is:
The telescopic folding-wing structure of the span described in the utility model is the compactest, and span amplitude of variation is big, is drawing in
Time by wing and lean against in the longitudinal direction of pedestal so that taking up room of storing minimizes, before the most left front inner wing and the right side
Interior flapwise pedestal both sides are launched, and utilize the outer wing length side of inner wing before left front inner wing and the right side respectively before left front outer wing and the right side simultaneously
Further increase span-width to stretching out, thus be effectively increased aircraft lift and lift-drag ratio, improve the flight effect of aircraft
Rate.
Accompanying drawing explanation
Fig. 1 is STRUCTURE DECOMPOSITION figure of the present utility model；
Fig. 2 is the structural representation of this utility model rounding state；
Fig. 3 is the structural representation that this utility model launches process；
Structural representation when Fig. 4 is that during this utility model launches, before left front outer wing and the right side, outer wing stretches out；
Fig. 5 is the structural representation that this utility model has launched.
Detailed description of the invention
Below in conjunction with the accompanying drawing in this utility model embodiment, the technical scheme in this utility model embodiment is carried out
Clearly and completely describe, it is clear that described embodiment is only a part of embodiment of this utility model rather than whole
Embodiment.Based on the embodiment in this utility model, those of ordinary skill in the art are not under making creative work premise
The every other embodiment obtained, broadly falls into the scope of this utility model protection.
A kind of telescopic folding wings of the span disclosed in this utility model embodiment, span amplitude of variation is big, obtains after spademan
Obtain large-sized wing, provide powerful lift for aircraft, wing can be drawn in completely when storing, less than fuselage width
Degree, reduces the most to greatest extent and takes up room.
As shown in Figures 1 to 5, a kind of telescopic folding wings of the span, including front wing, rear wing, pedestal 1 and actuating system 2,
Described front wing includes inner wing 4 before symmetrically arranged left front inner wing 3 and the right side, after rear wing includes the symmetrically arranged left back wing 5 and the right side
The wing 6, before left front inner wing 3 and the right side, the end of inner wing 4 is installed axle 7 by front wing and is hingedly mounted on pedestal 1 one end, another at pedestal 1
One end device actuating system 2, one end of the left back wing 5 and right rear wing 6 is hingedly mounted on slide block 9 by rear wing installation axle 8, slide block
9 are driven along pedestal 1 the most movable by actuating system 2, and the other end of the left back wing 5 and right rear wing 6 is respectively along left front inner wing 3 He
Before before right, the length direction of inner wing 4 slides and drives left front inner wing 3 and the right side, inner wing 4 launches or draws in；In order to increase the wing further
Broadening degree, is respectively provided with outer wing 11 before left front outer wing 10 and the right side, left front outer wing 10 He before left front inner wing 3 and the right side on inner wing 4
Before right, outer wing 11 slidably, the left back wing 5 and right rear wing 6 arranges biography along the length direction of inner wing 4 before left front inner wing 3 and the right side respectively
Before untie-sell 12 and left front outer wing 10 and the right side, outer wing 11 is articulated and connected, and under the promotion of slide block 9, the left back wing 5 and right rear wing 6 make a left side
Before front inner wing 3 and the right side, inner wing 4 launches to pedestal 1 both sides, and before the most left front outer wing 10 and the right side, outer wing 11 is respectively to left front inner wing 3 He
Before right, the length direction of inner wing 4 stretches out increase span-width.
Before left front inner wing 3 and the right side, before inner wing 4 and left front outer wing 10 and the right side, attachment structure between outer wing 11 can use multiple
Version makes outer wing 11 before left front outer wing 10 and the right side slide along the length direction of inner wing 4 before left front inner wing 3 and the right side respectively, and one
The mode of kind is to arrange inner chamber along its length, outer wing 11 points before left front outer wing 10 and the right side before left front inner wing 3 and the right side on inner wing 4
Other device slides in the inner chamber of inner wing 4 before left front inner wing 3 and the right side along its length；Another way is, left front outer wing 10 He
The periphery of inner wing 4 sliding along its length before outer wing 11 is wrapped in left front inner wing 3 and the right side respectively before right.
On pedestal 1, before left front inner wing 3 and the right side, the side of inner wing 4 expansion direction is provided with pedestal confined planes 20, left front
Before inner wing 3 and the right side, inner wing 4 installs axle 7 rotary expansion around front wing, and before left front inner wing 3 and the right side, the outer side edges of inner wing 4 is resisted against pedestal
Reaching the maximum span angle set time on confined planes 20, before preventing left front inner wing 3 and the right side, inner wing 4 is crossed and is rotated, it is ensured that in left front
Before the wing 3 and the right side, inner wing 4 keeps maximum span amplitude；On pedestal 1, it is provided with elastic limit device, elastic limit device position simultaneously
By front wing installation axle 7 and before left front inner wing 3 and the right side, inner wing 4 draws the side in direction in, and elastic limit device includes spring
Sheet 13 and limited block 14, pedestal 1 is offered groove, and spring leaf 13 is placed in groove, and limited block 14 is placed in groove and is pressed in spring
On sheet 13, and limited block 14 is connected on pedestal 1 by stop screw 15, and limited block 14 has up and down stroke, left front
Before inner wing 3 and the right side, inner wing 4 is when not up to maximum span state, and before left front inner wing 3 and the right side, limited block 14 is pushed down and made bullet by inner wing 4
Reed 13 compresses；When before left front inner wing 3 and the right side, inner wing 4 reaches maximum span state, limited block 14 is under spring leaf 13 acts on
Pop up the inner side edge of inner wing 4 before abutting against left front inner wing 3 and the right side and lock maximum span state, it is to avoid left front inner wing 3 and the right side
Front inner wing 4 resilience, it is ensured that in flight course, before left front inner wing 3 and the right side, inner wing 4 is in maximum span state all the time, and raising flies
Line stabilization.
Actuating system 2 includes start cylinder 21 and start push rod 22, and start cylinder 21 is fixed on pedestal 1, start push rod
22, along pedestal 1 longitudinal extension, pedestal 1 are provided with along longitudinal guide chute 16, and slide block 9 is edge under the effect of start push rod 22
Guide chute 16 slidably reciprocates, and actuating system 2 uses priming system, gases at high pressure, spring or motor to drive, according to practical flight device
Situation implement, easy to use and flexible.Slide block 9 is connected with start push rod 22 by contiguous block 17 simultaneously, and slide block 9 passes through slide block
Bearing pin 18 is hinged on contiguous block 17, and contiguous block 17 is hinged on start push rod 22 by connecting bearing pin 19, and slide block bearing pin
18 are axially mutually perpendicular to be connected bearing pin 19, form gimbal structure, it is achieved varied angle power transmits, and ensure start push rod pair
The active force of slide block is smooth fluent, is prevented effectively from the situation occurring that transmission is stuck, it is ensured that wing stably launches or draws in.
The telescopic folding wings of the span described in the utility model is when rounding state, and actuating system 2 is longitudinally received along pedestal 1
Before contracting makes left front inner wing 3 and the right side, inner wing 4, the left back wing 5 and right rear wing 6 respectively and are close together, before upper left front inner wing 3 and the right side in
The wing 4 also leans on, and before left front outer wing 10 and the right side, outer wing 11 is respectively superposed and is contracted in before left front inner wing 3 and the right side on inner wing 4, at pedestal 1
Center line on be provided with latch 23 so that under rounding state left front inner wing 3, right before at inner wing 4, the left back wing 5 and right rear wing 6
Midline position in pedestal 1；Upon deployment, actuating system 2 promotes slide block 9, the left back wing 5, right rear wing 6 along pedestal 1 longitudinal tensile strain
And left front inner wing 3, right before inner wing 4 launch to the both sides of pedestal 1 longitudinal direction, before left front outer wing 10 and the right side, outer wing 11 is respectively to left front
Before inner wing 3 and the right side, the length direction of inner wing 4 stretches out, when before left front inner wing 3 and the right side, the outer side edges of inner wing 4 is resisted against pedestal confined planes
Maximum span state is reached time on 20.
Below it is only preferred implementation of the present utility model, it is noted that above-mentioned preferred implementation should not regard
For to restriction of the present utility model, protection domain of the present utility model should be as the criterion with claim limited range.For
For those skilled in the art, without departing from spirit and scope of the present utility model, it is also possible to make some
Improvements and modifications, these improvements and modifications also should be regarded as protection domain of the present utility model.
Claims (10)
1. the telescopic folding wings of the span, including front wing, rear wing, pedestal (1) and actuating system (2), it is characterised in that institute
The front wing stated includes inner wing (4) before symmetrically arranged left front inner wing (3) and the right side, rear wing include the symmetrically arranged left back wing (5) and
Right rear wing (6), before left front inner wing (3) and the right side, the end of inner wing (4) is installed axle (7) by front wing and is hingedly mounted on pedestal (1)
End, at other end device actuating system (2) of pedestal (1), axle is installed by rear wing in one end of the left back wing (5) and right rear wing (6)
(8) being hingedly mounted on slide block (9), slide block (9) is driven along pedestal (1) the most movable by actuating system (2), the left back wing
(5) slide and drive left front along the length direction of inner wing (4) before left front inner wing (3) and the right side with the other end of right rear wing (6) respectively
Before inner wing (3) and the right side, inner wing (4) launches or draws in；When rounding state, actuating system (2) makes along pedestal (1) longitudinal contraction
Before left front inner wing (3) and the right side, inner wing (4), the left back wing (5) and right rear wing (6) respectively and are close together, before left front inner wing (3), the right side
Inner wing (4), the left back wing (5) and right rear wing (6) are positioned at the longitudinal direction of pedestal (1)；Upon deployment, actuating system (2) is indulged along pedestal (1)
Promoting slide block (9) to elongation, the left back wing (5), right rear wing (6) and left front inner wing (3), right front inner wing (4) are to pedestal (1) longitudinally
Both sides launch, left front inner wing (3), right before inner wing (4) around front wing, axle (7) is installed and rotates and reach maximum to the expanded angle set
Span state.
The telescopic folding wings of the span the most according to claim 1, it is characterised in that described left front inner wing (3) and the right side
It is respectively provided with on front inner wing (4) on outer wing (11) before left front outer wing (10) and the right side, the left back wing (5) and right rear wing (6) and biography is set
Before untie-sell (12) and left front outer wing (10) and the right side, outer wing (11) is articulated and connected, and outer wing (11) point before left front outer wing (10) and the right side
Not along inner wing (4) length direction slip before left front inner wing (3) and the right side under the drive of the left back wing (5) and right rear wing (6), in expansion
Time, before left front outer wing (10) and the right side outer wing (11) respectively before left front inner wing (3) and the right side length direction of inner wing (4) stretch out increase
Span-width.
The telescopic folding wings of the span the most according to claim 2, it is characterised in that described left front inner wing (3) and the right side
The upper inner chamber arranged along its length of front inner wing (4), before left front outer wing (10) and the right side, outer wing (11) device respectively is at left front inner wing
(3) and before the right side, the inner chamber of inner wing (4) slides along its length；Or outer wing (11) wraps up respectively before left front outer wing (10) and the right side
Inner wing (4) peripheral sliding along its length before left front inner wing (3) and the right side.
The telescopic folding wings of the span the most according to claim 1, it is characterised in that be provided with on described pedestal (1)
Elastic limit device, elastic limit device be positioned at front wing install axle (7) other and before left front inner wing (3) and the right side inner wing (4) receipts
Holding together the side in direction, elastic limit device includes spring leaf (13) and limited block (14), and pedestal offers groove, spring leaf on (1)
(13) being placed in groove, limited block (14) is placed in groove and is pressed on spring leaf (13), and limited block (14) is by spacing spiral shell
Nail (15) is connected on pedestal (1), and limited block (14) has up and down stroke, and before left front inner wing (3) and the right side, inner wing (4) is not
When reaching maximum span state, before left front inner wing (3) and the right side, limited block (14) is pushed down and is made spring leaf (13) compress by inner wing (4)；
When before left front inner wing (3) and the right side, inner wing (4) reaches maximum span state, limited block (14) spring leaf (13) act under upwards
The inner side edge of inner wing (4) before abutting against left front inner wing (3) and the right side of upspringing locks maximum span state.
The telescopic folding wings of the span the most according to claim 1, it is characterised in that left front on described pedestal (1)
Before inner wing (3) and the right side, the side of inner wing (4) expansion direction is provided with pedestal confined planes (20), before left front inner wing (3) and the right side in
The wing (4) installs axle (7) rotary expansion around front wing, and before left front inner wing (3) and the right side, the outer side edges of inner wing (4) is resisted against pedestal confined planes
(20) maximum span state is reached time above.
The telescopic folding wings of the span the most according to claim 1, it is characterised in that be provided with on described pedestal (1)
Along longitudinal guide chute (16), slide block (9) slides along guide chute (16).
The telescopic folding wings of the span the most according to claim 1, it is characterised in that described actuating system (2) includes
Start cylinder (21) and start push rod (22), start cylinder (21) is fixed on pedestal (1), and start push rod (22) is along pedestal (1)
Longitudinal extension.
The telescopic folding wings of the span the most according to claim 7, it is characterised in that described actuating system (2) uses
Priming system, gases at high pressure, spring or motor drive.
The telescopic folding wings of the span the most according to claim 7, it is characterised in that described slide block (9) is by connecting
Block (17) is connected with start push rod (22), and slide block (9) is hinged on contiguous block (17) by slide block bearing pin (18), contiguous block (17)
It is hinged on start push rod (22) by connecting bearing pin (19).
The telescopic folding wings of the span the most according to claim 9, it is characterised in that described slide block bearing pin (18) with
Connect axially being mutually perpendicular to of bearing pin (19).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620539010.7U CN205686604U (en) | 2016-06-01 | 2016-06-01 | A kind of telescopic folding wings of the span |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620539010.7U CN205686604U (en) | 2016-06-01 | 2016-06-01 | A kind of telescopic folding wings of the span |
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| Publication Number | Publication Date |
|---|---|
| CN205686604U true CN205686604U (en) | 2016-11-16 |
Family
ID=57259934
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
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| CN201620539010.7U Active CN205686604U (en) | 2016-06-01 | 2016-06-01 | A kind of telescopic folding wings of the span |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105818962A (en) * | 2016-06-01 | 2016-08-03 | 中电科（德阳广汉）特种飞机系统工程有限公司 | Foldable wing extensible in wingspan |
| CN112455653A (en) * | 2020-12-06 | 2021-03-09 | 西安长峰机电研究所 | Folding and unfolding mechanism for wing surface of aircraft |
| CN113665792A (en) * | 2021-08-11 | 2021-11-19 | 广东空天科技研究院 | Folding wing and locking mechanism suitable for high bearing state of folding wing |
-
2016
- 2016-06-01 CN CN201620539010.7U patent/CN205686604U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105818962A (en) * | 2016-06-01 | 2016-08-03 | 中电科（德阳广汉）特种飞机系统工程有限公司 | Foldable wing extensible in wingspan |
| CN112455653A (en) * | 2020-12-06 | 2021-03-09 | 西安长峰机电研究所 | Folding and unfolding mechanism for wing surface of aircraft |
| CN113665792A (en) * | 2021-08-11 | 2021-11-19 | 广东空天科技研究院 | Folding wing and locking mechanism suitable for high bearing state of folding wing |
| CN113665792B (en) * | 2021-08-11 | 2023-12-05 | 广东空天科技研究院 | Folding wing and locking mechanism suitable for high bearing state of folding wing |
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